Ventral segmented nozzles for promoting rapid temperature and pressure decay

Abstract

A thrust deflector system for VSTOL aircraft. The thrust directing system consists of a number of spaced-apart, downwardly facing openings along the bottom of the fuselage. The openings are fluidly connected with the outlet of the aircraft engine so that pressurized gas from the aircraft engine is discharged through the openings and away from the fuselage in discrete spaced-apart jets.

We claim: 
     
       1. A thrust directing system for VSTOL aircraft having a pressurized gas generator located in an engine bay, said pressurized gas generator having an outlet through which pressurized gas is discharged, said aircraft further having a fuselage, said thrust directing system comprising: a plurality of spaced-apart, downwardly facing openings along the bottom of said fuselage, said openings being fluidly connected with said outlet of said pressurized gas generator so enabling said pressurized gas being discharged through said pressurized gas outlet to be further discharged through said openings and away from said fuselage in discrete, spaced-apart jets; and, air introduction means fluidly communicating with said engine bay and the spaces between said openings for introducing air from said engine bay into said spaced between said openings.   
     
     
       2. A thrust directing system according to claim 1 wherein at least one of said openings is provided with at least one vectoring flap for further directing said jet being discharged from said opening, said flap being movable to direct said jet from a vertical direction to at least one rearwardly direction. 
     
     
       3. A thrust directing system according to claim 2 wherein each of said flaps is movable across said opening to close said opening. 
     
     
       4. A thrust directing system according to claims 1, 2 or 3 wherein said openings are generally rectangular and have a longitudinal axis extending across the bottom of said fuselage. 
     
     
       5. A thrust directing system according to claims 2 or 3 wherein: said openings are generally rectangular having a longitudinal axis extending across the bottom of said fuselage and having a forward side toward the front of said fuselage and a rearward side toward the rear of said fuselage, said forward and rearward sides being generally parallel to said longitudinal axis of said opening;   each of said openings being provided with a forward flap adjacent said forward side and a rearward flap adjacent said rearward side;   each of said flaps being rotatable about a rotational axis, said rotating axis being generally parallel to said longitudinal axis;   each of said flaps having a trailing edge distal and generally parallel to said rotational axis;   said flaps having a folded position wherein said forward flaps lie along said fuselage with said trailing edges of said flaps facing rearwardly and said rearward flaps lying across said adjacent openings; and,   said flaps are rotatable, from said closed position, about said rotational axis whereby said trailing edge moves forwardly in an arc depending below said fuselage at least so far as to be vertically below said rotational axis.   
     
     
       6. A thrust directing system according to claims 2 or 3 wherein: said openings are generally rectangular having a longitudinal axis extending across the bottom of said fuselage and having a forward side toward the front of said fuselage and a rearward side toward the rear of said fuselage, said forward and rearward sides being generally parallel to said longitudinal axis of said opening;   each of said openings being provided with a forward flap adjacent said forward side and a rearward flap adjacent said rearward side;   each of said flaps being rotatable about a rotational axis generally parallel to said longitudinal axis;   each of said flaps having a trailing edge distal and generally parallel to said rotational axis;   said flaps having a folded position wherein said forward flaps lie along said fuselage with said trailing edges of said flaps facing rearwardly and said rearward flaps lying across said adjacent openings; and,   said flaps are rotatable, from said closed position, about said rotational axis whereby said trailing edge moves forwardly in an arc depending below said fuselage at least so far as to be vertically below said rotational axis; and,   wherein said openings have a length to thickness ratio of from 10 to 20 and said openings have a pitch to thickness ratio of from 3 to 10.